Iland



Patented Oct. 14,1919.

2 SQIEETS-SHET 1- J0 S T M w w 9 1 n q H 1 8 r r 4 2 H M uwnmhnwi f 3 w H 3 4A 7 v w M Z Z 4 M. n..- a --.w.. a

04 a. 6 am n a K a U 6. DE HAVILlAND AND J. S. CHAPMAN.

FUEL SUPPLY PUMP FOR MROPLANE ENGINES AND THE LIKE.

Armenian FILED was. ms. 1,318,732.

ll IHP l-i min in mnumum 11)., vmsumn'ron. n. n

6. DE HAVILLAND AND J. S. CHAPMAN. FUEL SUPPLY PUMP ron AEROPLANE ENGINES AND THE LIKE. APPLICATION FILED 16.5. I918.

1,318,732. Patented Oct. 14,1919.

lnventoys Q7 iii MM pass outward through the sidewall of the stool 32, beyond which the pipe is detachably coupled by a screw-union 42 to a pipe 43 leadi to the carhureter of the engine.-

.-In e course of the upright :pipe 40 are interposed a relief valve and a non-return which are shown in outside elevation in Fig. l and in sectionakdetail'in Fig; 2.. The re= oonoidal trumpet-mouth 4% on the lower on of a sleeve 45 which it fitted to slide over the pipe 40, the lower margifrof thetrulfipetmouth 44 constituting the valve-face which normally"closes against a fix'ed"seatin 46 provided-upon a flanged? which pro ects radially around a section of the pipe 40" suported in a pair of upper and lower brackets 28, 49 fixed to the pump carrying tube 13, while immediately above the flange 47 a series of apertures 50 in the wall of the ipe 40 open from the interior of the latter lnto the s 'ace 51 inclosed between the pipe and the trumpet-mouth 44 are pressed downward, so as normally to hold the relief Valve closed, by. a spring 52 coiled in compression about the sleeve 45 and pipe 40 between the outer surface of the trumpet-month y]: and the upper bracket 48, so that,,on the pressure Within the pipe {l0 and space 51fexceeding the resistance due to the spring-'52, the valve will be forced upward and;allow the escape of the liquid fuel from the pipe.

Above the bracket '48, the, upright'pipe [4G is provided with a local enlargement 53 constituting a chamber forth accommodation of the non-return. valve, hih comprisesn ball 54 normall" resting by gravity upon a seat 55 surround 21g the mouth of the pipe 40 within the chamber 53, the twopins or wires represented by the small circles 56,

extending transversely of the chamber 53, some distance aboyethe uorn'ral position of the ball '54, forminga sto" to limit the upward movement of the hall.

It will be seenthat the above described construction permits readylreruoval from the tank 3 of the pump :11, pump-carrying tube 13, aeroznotor 28, and gearfcase -BI with h i i ed e adi'i n all as a s fo m n un t, when, h p e s b en coplpled from the p'ilpe" 3 atlihe union 42 an the clamping-be ts 17 have been unfase ed-r 1. In an aeroplane or the like, provided with, a v ffi el supply ta kfle a sarbur e or. sub idi ry,y aid ain tank having a. flange opening, means or trailsjarring; fuel from the main the-carll rsbbr l sflb diait. eak, c ihpriising and, inseminated r m, t organ u mal lta k, a ia r d r'fi h i inpi disg man tank and an aeromotor or" thelike power lief valve comprises a downwardly-flaringrumpet-m'o'uth. The sleeve. 45 and i 4 1 a i 4 a 1s located,, s,a 1d main tank: bemg provlde withanopening opposite saidfwell, a cover element for continuously operating said pump while the aeroplane is fiyin said pump, the discharge pipe, and sai aeromotor being mounted u on and supported by a cover-plate adapte to fit said flanged opening, thereby adapting them to be removed as a unit, and means for securing thecover plate to the flanged opening, substantially as described.

2. In an aeroplane or the like, rovided with a main fuel suppl tank an i a carbureter'or subsidiary tan means for trans ferring fuel from the main tank to the carbureter or subsidiary tank, com rising a pump supported in the main tank y a tube adapted to inclose thedriving shaft of the pump, a well in the main tank in which said pump, is located, said main tank being rovided with an opening opposite said we 1, a cover plate for said opemng with which said pump supporting tube is connected, an aeromotor mounted u on said cover plate and geared to said she t for o erating said pump and a discharge pipe lea ing from the pump through said cover plate and adapted to be connected with said carburetor or subsidiary tank, ,substantiall as described.

' 3; In an aero. lime or the like, provided with a main fue'" supply tank and a carbureter' or subsidiary tank,said main tank having a flanged opening, means for transferring' fuel from the'main tank tolthecarbureter or subsidiary tank, comprising a pump suspended within the through sa1 opening therein, a cover plate supporting said pump and adapted for closing said cover plate, an aeromotor connected by gearing with said shaft and a gear-case of stream -line configuration mounted upon said covenplate and mclosing said gearing substantially as described.

4:. In anaeroplaneor the like, rovided with a mainjfuel supply tank an a carbureter'or subsidiary tank, said main tank having an opening therein and a tank-well below and o pos'lte said openin a cover platejforsaislopening, a pump coated in said tank-well -and suspended from said cover plate, pin and socket engagin r means between thepump and said tank-w land a motor supported on said cover plate for drivipcgfsalfl P mp, substantially as de- 5, In an. aeroplane o'r the like, provided with as main vfuel. supply and a carbureteror subsidiarytaiik; means for transferri 'rg'; i1e1]from' thefiuain tank to the carburete or subsidiary-tank, 'a pump supported in themam ta aj'tu adapta a 2 9 9 ha ifi as s a f th Pu p, well ln the ma n tank m. which said; pum

s te fps-said r amsith h h said P mp supporting tube" 1s connected, an aeromotor mounted upon said cover plate and geared to said shaft for operating said pump, a discharge pipe leadm from the pump through said cover plate an adapted to be connected with said caibureter a spring actuated relief valve in said discharge pipe, substantially as described.

6 In an aeroplane or the like, provided with a main fuel supply tank and a carbureter or subsidiary tank, means for transferring fuel from the main tank to the carbureter or subsidiary tank, oomprisin a pump supported in the main tank by a tu e adapted to inclose the driving shaft of the pump, a well in the main tank in which said pump is located, said main tank being provided with an opening opposite said well, a cover plate for said opening with which said pump supporting tube is connected, an aeromotor mounted upon said cover plate and geared to said shaft for 0 crating said pump, a discharge pipe leadmg from the pump through said cover plate and adapted to be connected with said carbureter or su sidiary tank, and a non-return valve inter- Ooples at this patent may be obtained 1'0: five cents each,

Washington,

or subsidiary tank, and 4 ferring fuel from the main tank to the carbureter or subsidiary tank, comprising a pump supported in the main tank y a tube adapted to inclose the driving shaft of the pump, a well in the main tank in which said pump is located, said main tank bein provided with an o ening opposite sai well, a cover plate or said openin with which said pump supporting tube is connected, an aeromotor mounted upon said cover plate and geared to said shaft for operating said pump, a discharge pipe leading from the pump through said cover plate and adapted to be connected with said carbureter or subsidiary tank, a spring actuated relief valve and a non-return valve suitably interposed in said discharge tially as described GEOFFREY on HAVILLAND. JOHN STANTON CHAPMAN.

by addressing the Oommissioner of Patents, D. 0."

pipe, substam 

